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X2LH =
X2RH =
Finding Empty - Weight Center of Gravity (XCG): Empty Weight CG Formula: (G1 x X1)+(G2LH x X2LH)+(G2RH x X2RH)XCG = G1 + G2LH + G2RH
Finding Empty - Weight Moment:
Empty-weight Moment (M) = Empty Weight (G) x Empty-weight CG
(Positive results indicate, that CG is located aft of RD)
Finding Maximum Permitted Useful Load:
Maximum Weight [kg] (lbs) 800 kg/1764 lbs
Empty Weight [kg] (lbs)
Maximum useful Load [kg] (lbs)
Empty Weight (G): ([kg]) (lbs) Empty-weight Moment (M): ([kg.m]) (in.lbs)
Place / Date Authorizing Stamp Authorizing Signature
Figure 6.3. Weighing Report
Doc # DA202-C1 April 06, 2010 Page S4 - 14
Revision 25 DOT Approved
Calculation of the Load Limits DA 20 (Example) Your DA 20
Weight [lbs] (Weight [kg]) Moment [in.lbs] ([kgm]) Weight [lbs] (Weight [kg]) Moment [in.lbs] ([kgm])
1. Empty Weight (use the data for your airplane recorded in the equipment list, including unusable fuel and lubricant). 1153 (523) 12562 (144.740)
2. Pilot and Passenger: Lever Arm: 0.143 m (5.63 in) 359 (163) 2021 (23.286)
3. Baggage: Max. Wt. 44 lbs (20 kg) Lever Arm: 0.824 m (32.44 in) --(--) --(--)
4. Baggage Compartment Extension: Max. Wt. 44 lbs (20 kg) Lever Arm: 1.575 m (62.0 in) --(--) --(--)
5. *Combined Baggage Max. Wt. 44 lbs (20 kg) Lever Arm: 1.20 m (47.22 in) --(--) --(--)
6. Total Weight and Total Moment with empty fuel tank (sum of 1. - 3.) 1512 (686) 14583 (168.026)
7. Usable Fuel Load (6.01 lbs. per US gal./0.72 kg per liter) Lever Arm (32.44 in) (0.824 m) 93 (42) 3017 (34.762)
8. Total Weight and Total Moment, taking fuel into account (sum of 6. and 7.) 1605 (728) 17600 (202.788)
9. Find the values for the total weight (1512 lbs and 1605 lbs) and the total moment (14583 in lbs and 17600 in. lbs) in the center of gravity diagram. Since they are within the limitation range, the loading is permissible.
Figure 6.6. Calculation of Loading Condition
* Combined Baggage: For convenience of calculation use this line if baggage is to be located in both the baggage compartment and the baggage extension. The combined total of the baggage must not exceed 44 lbs (20 kg).
Doc # DA202-C1 April 16, 2009 Page S4 - 15
Revision 24 DOT Approved
See example calculation of loading condition Figure 6.6. Change in center of gravity is due to fuel consumption
Figure 6.7. Permissible Center of Gravity Range and Permissible Flight-Weight-Moment
7. DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS
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